ADCS Systems

34 ADCS Systems for Space Applications from 9 manufacturers listed on SatNow

ADCS Systems for space applications from multiple manufacturers are listed on SATNow. Use the filters to select products based on your requirement. View product details, download datasheets, compare products, get quotes and pricing for matching products. SATNow has compiled this list of products specifically for Space and Satellite Applications.

SKU:iADCS200
Satellite Type:
CubeSat, SmallSat
Component:
Reaction Wheel, Magnetorquer, Inertial Measurement Unit
Mass:
0.4, 0.435, 0.47 kg
Torque:
0.087 mNm
Momentum:
+/- 1.5, +/- 3.0, +/- 6.0 mNms
Pointing Accuracy:
1 deg
Supply Voltage:
4 to 15 V
Power Consumption:
Idle: 1150 mW, Nominal: 1400 mW
Radiation Tolerance:
45 krad (Si)
Slew Rate:
1.52 deg/sec
Space Heritage:
Yes
Data Interface:
I2C, RS-422, RS-485, UART, CAN
more info
Description:The LEOS platform and allows full ADCS functionality including nadir pointing as well as autonomous target acquisition and tracking
Satellite Type:
CubeSat
Component:
Reaction Wheel, Magnetorquer, Star Tracker, Gyroscope, Magnetometer, Accelerometer
Mass:
0.4 kg
Pointing Accuracy:
1 deg
Power Consumption:
1150 mW
Space Heritage:
Yes
Data Interface:
RS-485, I2C, RS-422
more info
SKU:XACT-15
Satellite Type:
CubeSat
Mass:
1.1 Kg
Torque:
5 mNm
Momentum:
15 mNms
Volume:
0.5 U
Pointing Accuracy:
±0.003 deg (1-sigma) for 2 axes ±0.007 deg (1-sigma) for 3rd axis
Supply Voltage:
12 V
Radiation Tolerance:
40 Krad
Slew Rate:
Up to 10 Deg/sec (4 kg 3U Cubesat)
Data Interface:
RS-422
Spacecraft Lifetime:
5 Years
more info
SKU:CubeADCS Y-Momentum
Satellite Type:
NanoSat
Component:
Magnetometer, Coarse Sun Sensors, Fine Sun & Earth Sensors, Star Tracker
Mass:
0.3 Kg
Space Heritage:
Yes
more info
SKU:Arcus ACDS (KU Leuven ADCS)
Satellite Type:
CubeSat
Component:
Gyroscope, Photodiode, Magnetometer, Star Tracker, Reaction Wheel, Magnetorquer, PID Controller, Coarse Controller
Mass:
0.715 kg
Torque:
0.5 mNm (RW torque)
Momentum:
4 mNms ( R.W Momentum Capacity)
Pointing Accuracy:
0.11 (Fine, Fine) to 6.3 (Coa, Coa) deg
Supply Voltage:
3.3 to 5 V
Power Consumption:
940 (Detumbling) to 1400 mW (Fine/Fine)
Slew Rate:
60 deg/sec
Data Interface:
I2C, CAN
Spacecraft Lifetime:
3 Years
more info
SKU:D-Sense
Component:
Photodiode, Thermopile, Magnetometer, Gyroscope, Camera
Mass:
0.2 kg
Power Consumption:
300 mW (Standard Operative mode), 500 mW (Camera Mode)
Data Interface:
CAN
more info
SKU:ADCS-10m
Satellite Type:
NanoSat, MicroSat
Component:
Magnetorquer, Gyroscope
Mass:
0.44 Kg
Torque:
13 mNm
Momentum:
13 mNms
Volume:
0.7 U (Cube) or 1 Tuna-can & 0.25 U
Pointing Accuracy:
0.4 Degrees
Supply Voltage:
3.3 to 5 V
Power Consumption:
2.7 W
Radiation Tolerance:
24 krad
Slew Rate:
5 Degree/sec
Space Heritage:
Yes
Data Interface:
RS-485, UART
Spacecraft Lifetime:
3 Yrs
more info
SKU:iADCS400
Satellite Type:
CubeSat, SmallSat
Component:
Reaction Wheel, Magnetorquer, Sun Sensor, GNSS Receiver, Gyroscope
Mass:
1.150, 1.300, 1.700 kg
Torque:
2 mNm
Momentum:
+/- 1.5, +/- 3.0, +/- 6.0 mNms
Pointing Accuracy:
1 deg
Supply Voltage:
4.9 to 15 V
Power Consumption:
Idle: 900 mW(2400 mW), Nominal: 2000 mW
Radiation Tolerance:
45 krad (Si)
Slew Rate:
1.57 deg/sec
Data Interface:
I2C, RS-422, RS-485, UART, CAN
more info
Description:High-performance design compatible with a wide range of satellite configurations
Mass:
Configuration Dependent
Momentum:
B/w 500 and 8000 mNms depending on which wheels are used
Pointing Accuracy:
±0.002 deg (1-sigma), 3 axes
Supply Voltage:
5, 28 V
Slew Rate:
Application Dependent
Data Interface:
RS-422
Spacecraft Lifetime:
5 Years
more info
SKU:CubeADCS 3-Axis Small
Satellite Type:
NanoSat
Component:
Magnetometer, Coarse Sun Sensors, Fine Sun & Earth Sensors, Star Tracker
Mass:
0.5 Kg
Space Heritage:
Yes
more info

What are Attitude and Determination Control Systems (ADCS)?

Attitude Determination and Control System (ADCS) is a crucial subsystem of any spacecraft that controls the attitude and orientation of the spacecraft and provides pointing accuracy and stability for the payload of the spacecraft. It operates based on the information it receives from the ground as well as its onboard sensors. Every spacecraft has 6 degrees of freedom (DOF) which indicates the movement of a spacecraft in a three-dimensional space. Three of them are displacement, and the rest of them are rotation. The altitude determination and control system (ADCS) is responsible for the 3 DOF rotational control of the spacecraft.


ADCS consists of four different segments:

  • Sensor System: The sensor module is mainly used for attitude determination. Some of the common altitude sensors that the satellite use is (coarse/fine) sun sensorearth sensor, IMU, star tracker, and geomagnetic sensor.
  • Actuator System: The actuator system is used for attitude control and is used to position the spacecraft in the target attitude by rotating it in 3-axes (yaw, roll, and pitch). Some of the most common ones are the reaction wheelcontrol moment gyroscope (CMG)thruster, and magnetorquer
  • Controller: The ADCS Controller will calculate the attitude of the spacecraft using the data coming from the sensors. The Algorithm inside the controller will calculate the targeted attitude and will also determine the rotations needed to accomplish for each axis.
  • Interface: The ADCS Interface is the hardware part of ADCS that transmits the signal received from Sensors to the micro-controller and it also distributes the power supply coming from the EPS subsystem to the Actuators.

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